Abstract: The invention provides a method of assisting masking a part (100), the method comprising, prior to working on the part, the steps of: using a numerical model (1) of the part to define at least one virtual surface (2) for masking by extracting from the model a geometrical surface of the part that is to be masked, and by duplicating said geometrical surface; and assigning instructions (3) about masking to the virtual surface for masking as defined in this way; then when an operator is working on a part matching the numerical model, taking at least one image of the part and enabling the operator to view the image of the part with the virtual surface for masking superposed thereon while also displaying the associated instructions; and after the part matching the numerical model has been masked, taking an image of the masked part and comparing on the image the real masked surface with the virtual surface for masking.

Abstract: Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes: a spool configured to move axially inside the hydraulic valve; and a sleeve configured to at least partially house the spool. A location of the spool with respect to the sleeve may determine a flow of a working fluid through the hydraulic valve. A viscous damper is at least partially housed inside an opening in the spool, and a viscous friction between the viscous damper and the opening in the spool slows a motion of the spool.

Abstract: The invention provides a method of moving an aircraft undercarriage comprising a leg (1) that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut (2) held in an aligned position by a stabilizer member (4), the method including using a drive actuator (10) for raising the undercarriage from the deployed position to the retracted position. According to the invention, the actuator is coupled firstly to the leg and secondly to the stabilizer member in such a manner that on being activated the actuator begins by causing the stabilizer member to unlock and then moves the undercarriage leg towards the retracted position.

Abstract: A ground movement system for a land transport vehicle (2) capable of levitating, the vehicle having a plurality of wheels including at least one actuated wheel (3), a drive device (6) for driving the actuated wheel and/or a brake (8) for braking the actuated wheel (3), a vertical positioning actuator (9) arranged to move the actuated wheel (3) vertically relative to a fuselage of the vehicle (2), and control means arranged to act, during an acceleration stage and/or during a braking stage of the vehicle, to control the vertical positioning actuator (9) as to adjust the vertical position of the actuated wheel in order to increase the load carried by the actuated wheel and thus increase the maximum force that can be transmitted to the ground by the actuated wheel so as to increase the maximum drive and/or braking torque that can be produced by the drive device (6) and/or by the brake (8) without the actuated wheel (3) skidding or slipping.

Abstract: An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

Abstract: A system for measuring parameters of a mounted assembly comprises an electronic device for measuring parameters of the mounted assembly and a bonding interface made of elastomeric material surrounding the electronic device. The measuring electronic device comprises: a UHF radiofrequency antenna; and an electronic board with an electronic chip coupled to the UHF radiofrequency antenna, a sensor for measuring parameters of the mounted assembly, a microcontroller and an electrical circuit. The measuring system comprises a ground plane connected to the electronic board. The electronic board comprises an energy manager and a capacitive element. The coupling between the electronic chip and the UHF radiofrequency antenna is of an electrical nature. The electronic chip, the microcontroller and the measuring sensor are components of low energy consumption.

Abstract: Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows.

Abstract: A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.

Abstract: A method for engaging a first gear element with a second gear element is provided. The second gear element is mounted to be mobile between a meshing position and a position of disengagement using an actuator. The method includes driving one or more of the first and second gear elements in rotation to form a non-zero rotation speed difference between the first and second gear elements and controlling the actuator to successively displace the second gear element to the meshing position, and when an intermediate position of the second gear element is detected, stop the displacement of the second gear element, and when an angular position of engagement of the first and second gear elements is detected, displace the second gear element to the meshing position.

Abstract: A landing gear system includes a wheel rotatably coupled to an axle about an axis. A torque tube is rotatably mounted to the axle about the axis such that the axle extends through a central portion of the torque tube. A rotor is fixed in rotation about the axis relative to the wheel, and a stator is fixed in rotation about the axis relative to the torque tube. The landing gear assembly further includes a clutch assembly selectively reciprocal between an engaged state and a disengaged state. The stator is fixed in rotation about the axis relative to the torque tube when the clutch assembly is in an engaged state. When the clutch assembly is in a disengaged state, the stator is rotatably about the axis relative to the torque tube.

Abstract: A thermal actuator includes a piston slidingly within a cylinder. The piston cooperates with the cylinder to define a cavity. The piston also includes a rod extending away from the cavity. A magnetic field generator selectively imparts an alternating magnetic field to the cylinder, and inductively heats a heating element mounted within the cavity. The cavity also includes a volume of a phase-change material, which is melted by the heating element. The melting phase-change material expands to drive the rod from a retracted position to an extended position.

Abstract: A method of forming an annular textile preform by needling a helical fiber sheet includes in succession: unwinding a helical fiber sheet from a horizontal sheet-forming turntable driven at a constant and predefined speed of rotation NFS onto a horizontal intermediate unwinder driven at a speed of rotation NDI and positioned on a horizontal intermediate turntable driven at a speed of rotation NFI, unwinding the helical fiber sheet from the intermediate unwinder onto a final horizontal unwinder driven at a speed of rotation NDF, and unwinding the fiber sheet from the final unwinder onto a horizontal preform-forming turntable driven at a variable and predefined speed of rotation NFP so as to be subjected to needling thereon. The speeds NDI, NFI, and NDF are controlled in such a manner that NDF is proportional to NFP, NFI=(NFS?NDF)/2, and NDI=(NFS+NDF)/2.

Abstract: Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.

Abstract: An aircraft landing gear includes a strut leg, a bottom portion carrying at least one wheel and mounted to slide in the strut leg, and a plurality of elements such as power electric cables, signal-carrying electric cables, and hydraulic pipes extending toward the bottom portion along the strut leg and terminating at the bottom portion, all of the elements being flexible between a bottom end of the strut leg and the bottom portion of the landing gear. The landing gear includes a first movable support having a proximal end hinged to the bottom end of the strut leg, and a distal end carrying a rack for receiving and guiding the flexible elements. The landing gear also includes a second movable support having a distal end hinged to the bottom portion of the landing gear and a proximal end carrying a rack for receiving and guiding the flexible elements.

Abstract: A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.

Abstract: A passive lateral stability system maintains the position of a vehicle relative to a guideway. The system includes first and second guide assemblies that urge the vehicle away from first and second electrically conductive guide walls, respectively. The first guide assembly includes a wheel configured to reciprocate toward and away from the first guide wall. A biasing element bias biases the wheel toward the first guide wall. The system further includes a magnetic element associated with the wheel, wherein movement of the magnetic element relative to the first guide wall produces a magnetic force that biases the wheel away from the first guide wall. A second guide assembly is mounted to the vehicle and urges the vehicle away from the second guide wall.

Abstract: A measurement device for measuring the pressure of a wheel (3) of a vehicle, the measurement device comprising a stationary portion (5) and a movable portion (14) for being driven in rotation by the wheel, the stationary portion including a first printed circuit (7) having at least one first track formed thereon defining a first winding, the movable portion including a second printed circuit (16) having at least one second track formed thereon defining a second winding, the second printed circuit being arranged to be connected to a pressure sensor (15), the first winding and the second winding being coupled together to form a wireless communication channel, the measurement device being arranged in such a manner that the pressure sensor is electrically powered by the stationary portion via the wireless communication channel, and in such a manner that uplink data comprising pressure measurement data is transmitted to the stationary portion (5) by the movable portion (14) via the wireless communication channel.

Abstract: An aircraft landing gear assembly comprising: a ground contacting part, an aircraft attachment part, and a component comprising: a first base member and a second base member separated along a first longitudinal axis, a plurality of first connecting points on the first base member arranged in a first regular polygon, a plurality of second connecting points on the second base member arranged in a second regular polygon, the second regular polygon having the same number of sides as the first regular polygon, and a plurality of first straight beams fixed to the first and second base members at the first and second connecting points and extending between the first and second base members, each beam aligned skew to the longitudinal axis.

Abstract: A pressure measurement device (1) comprising a housing (20) extending around an electronic card (30) provided with a pressure sensor (40); the housing (20) co-operating with a first face (31) of the electronic card (30) to define a first sealed volume (3); the housing (20) also co-operating with a second face (32) of the electronic card (30) that is opposite from the first face (31) to define a second sealed volume (4); the housing (20) including at least one first channel (24) putting the medium (5) outside the housing (20) into fluid flow communication with the first sealed volume (3); the electronic card (30) including at least one second channel (33) putting the first volume (3) into fluid flow communication with the second volume (4); and the connection between the housing (20) and the electronic card (30) being arranged to allow relative movement between the housing (20) and the electronic card.

Abstract: An aircraft undercarriage carrying at least two wheels (4) and for mounting on an aircraft structure to be movable between a deployed position and a retracted position, the undercarriage being characterized in that the wheels are rotatably mounted on axles (3) carried by arms (2) hinged to a bottom portion of a strut-leg (1) of the undercarriage, each arm being associated with a shock absorber (5) coupled firstly to the arm and secondly to a collar (6) that extends around the strut-leg and that is mounted to slide on the strut-leg between a high position in which the collar bears against an abutment (7) of the strut-leg when the undercarriage is in the deployed position and a low position into which the collar is taken when the undercarriage is moved from the deployed position to the retracted position, so as to bring the wheels closer together.